CA2660964C - Moulding tool and method of manufacturing a part - Google Patents
Moulding tool and method of manufacturing a part Download PDFInfo
- Publication number
- CA2660964C CA2660964C CA2660964A CA2660964A CA2660964C CA 2660964 C CA2660964 C CA 2660964C CA 2660964 A CA2660964 A CA 2660964A CA 2660964 A CA2660964 A CA 2660964A CA 2660964 C CA2660964 C CA 2660964C
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- CA
- Canada
- Prior art keywords
- tool
- mould line
- inner mould
- tools
- mandrel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
- B29C43/021—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles characterised by the shape of the surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/30—Mounting, exchanging or centering
- B29C33/306—Exchangeable mould parts, e.g. cassette moulds, mould inserts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
- B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
- B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
- B29C33/485—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling cores or mandrels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
- B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
- B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
- B29K2105/0809—Fabrics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
- B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
- B29K2105/0872—Prepregs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/24—Moulded or cast structures
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
A tool set comprising: a moulding tool comprising a moulding surface and a mandrel recess in the moulding surface; a first mandrel configured to fit into the mandrel recess and form a first component; and a second mandrel configured to fit into the mandrel recess and form a second component which has a different shape or size to the first component.
A method of manufacturing a part, the method comprising: arranging a set of components on one or more inner mould line tools; forming a layer around the inner mould line tool(s);
fitting a pair of outer mould line tools on opposite sides of the inner mould line tool(s);
moulding the part by compressing the layer and the components between the inner and outer mould line tools; and removing the inner mould line tool(s) from the part.
A method of manufacturing a part, the method comprising: arranging a set of components on one or more inner mould line tools; forming a layer around the inner mould line tool(s);
fitting a pair of outer mould line tools on opposite sides of the inner mould line tool(s);
moulding the part by compressing the layer and the components between the inner and outer mould line tools; and removing the inner mould line tool(s) from the part.
Description
MOULDING TOOL AND METHOD OF MANUFACTURING A PART
FIELD OF THE INVENTION
The present invention relates in its various aspects to a moulding tool, a tool set, a method of manufacturing a moulding tool, and a method of manufacturing a part such as a composite part.
BACKGROUND OF THE INVENTION
US 5902535 describes an inner mould line (IML) tool for resin film infusion moulding a component in a single-step moulding operation. The IML tool comprises a plurality of mandrels in a modular design. The mandrels may be individually assembled over a preform assembly, such that the surface configurations on the underside of the mandrels match with the stringers and intercostals of the preform assembly.
SUMMARY OF THE INVENTION
A first aspect of the invention provides a moulding tool comprising a moulding surface, and a mandrel recess in the moulding surface, wherein the mandrel recess has a mandrel locator configured to engage with a mandrel so as to locate the mandrel at a desired position in the mandrel recess.
Providing a mandrel recess in the moulding surface enables a mandrel to be fitted easily and accurately relative to the moulding surface.
Typically the mandrel locator is configured to engage with the mandrel by means of a male/female connection (such as a hole or pin).
A plurality of mandrel recesses may be formed in the moulding surface, which is typically a contiguous piece of material. Thus each mandrel recess can be used to receive a mandrel for a respective component such as a stringer, or an additional component such as a spar, rib foot or rib post.
The tool may have only a single moulding surface on one side - for example for forming a half wing-box. Alternatively the tool may have a second moulding surface (either adjacent to or opposite to the first moulding surface); and one or more mandrel recesses in the second moulding surface, each configured to receive a respective mandrel. In this case the tool can be used to form a tubular part such as a full wing-box.
Typically each recess has been formed by removing material from the moulding tool - for instance by machining from a billet.
A further aspect of the invention provides a tool set comprising:
a moulding tool according to the first aspect of the invention;
a first mandrel configured to fit into the mandrel recess and form a first component;
and a second mandrel configured to fit into the mandrel recess and form a second component which has a different shape or size to the first component.
Thus the tool can be used in a modular tool set, in which a variety of mandrels can be interchangeably fitted into the mandrel recess(es) to form a desired component.
A further aspect of the invention provides a tool set comprising:
a moulding tool according to the first aspect of the invention;
two or more stringer mandrels each configured to fit into a respective one of the stringer mandrel recesses and form a respective stringer; and one or more additional mandrels each configured to fit into a respective one of the additional mandrel recesses and form a respective additional component.
Thus the moulding tool can accommodate mandrels for stringers and also for additional components such as rib feet, spars and/or rib posts.
FIELD OF THE INVENTION
The present invention relates in its various aspects to a moulding tool, a tool set, a method of manufacturing a moulding tool, and a method of manufacturing a part such as a composite part.
BACKGROUND OF THE INVENTION
US 5902535 describes an inner mould line (IML) tool for resin film infusion moulding a component in a single-step moulding operation. The IML tool comprises a plurality of mandrels in a modular design. The mandrels may be individually assembled over a preform assembly, such that the surface configurations on the underside of the mandrels match with the stringers and intercostals of the preform assembly.
SUMMARY OF THE INVENTION
A first aspect of the invention provides a moulding tool comprising a moulding surface, and a mandrel recess in the moulding surface, wherein the mandrel recess has a mandrel locator configured to engage with a mandrel so as to locate the mandrel at a desired position in the mandrel recess.
Providing a mandrel recess in the moulding surface enables a mandrel to be fitted easily and accurately relative to the moulding surface.
Typically the mandrel locator is configured to engage with the mandrel by means of a male/female connection (such as a hole or pin).
A plurality of mandrel recesses may be formed in the moulding surface, which is typically a contiguous piece of material. Thus each mandrel recess can be used to receive a mandrel for a respective component such as a stringer, or an additional component such as a spar, rib foot or rib post.
The tool may have only a single moulding surface on one side - for example for forming a half wing-box. Alternatively the tool may have a second moulding surface (either adjacent to or opposite to the first moulding surface); and one or more mandrel recesses in the second moulding surface, each configured to receive a respective mandrel. In this case the tool can be used to form a tubular part such as a full wing-box.
Typically each recess has been formed by removing material from the moulding tool - for instance by machining from a billet.
A further aspect of the invention provides a tool set comprising:
a moulding tool according to the first aspect of the invention;
a first mandrel configured to fit into the mandrel recess and form a first component;
and a second mandrel configured to fit into the mandrel recess and form a second component which has a different shape or size to the first component.
Thus the tool can be used in a modular tool set, in which a variety of mandrels can be interchangeably fitted into the mandrel recess(es) to form a desired component.
A further aspect of the invention provides a tool set comprising:
a moulding tool according to the first aspect of the invention;
two or more stringer mandrels each configured to fit into a respective one of the stringer mandrel recesses and form a respective stringer; and one or more additional mandrels each configured to fit into a respective one of the additional mandrel recesses and form a respective additional component.
Thus the moulding tool can accommodate mandrels for stringers and also for additional components such as rib feet, spars and/or rib posts.
2 A further aspect of the invention provides a method of manufacturing a part, the method comprising:
forming a component on a mandrel;
fitting the mandrel into a mandrel recess of a moulding tool;
arranging a panel with a first portion of the panel engaging a moulding surface of the moulding tool and a second portion of the panel engaging the component on the mandrel;
bonding the first portion of the panel to the component by compressing them against the first mandrel; and moulding the second portion of the panel by compressing it against the moulding surface of the moulding tool.
The panel may be a variety of elements, depending on the application. In the preferred embodiments described below, the panel is either a wing skin or part of a capping layer which is wrapped around the moulding tool.
A further aspect of the invention provides a method of manufacturing first and second parts, the method comprising:
manufacturing the first part by:
arranging a first component on a first mandrel;
fitting the first mandrel into a mandrel recess of a moulding tool;
arranging a first panel with a first portion of the panel engaging a moulding surface of the moulding tool and a second portion of the panel engaging the first component on the first mandrel;
bonding the first portion of the panel to the first component by compressing them against the first mandrel; and 21849951.2 3 moulding the second portion of the panel by compressing it against the moulding surface of the moulding tool;
removing the first mandrel from the mandrel recess; and manufacturing the second part by:
arranging a second component on the second mandrel;
fitting the second mandrel into the mandrel recess of the moulding tool;
arranging a second panel with a first portion of the panel engaging the moulding surface of the moulding tool and a second portion of the panel engaging the second component on the second mandrel;
bonding the first portion of the panel to the second component by compressing them against the second mandrel; and moulding the second portion of the panel by compressing it against the moulding surface of the moulding tool.
A further aspect of the invention provides a method of manufacturing a part, the method comprising:
arranging a set of components on a moulding tool; and simultaneously compressing the set of components on the moulding tool against a panel so as to bond the components to the panel, wherein the set of components includes a plurality of stringers, and one or more additional components.
In one embodiment of the invention, the method further comprises:
arranging a second set of components on the moulding tool; and compressing the second set of components on the moulding tool against a second panel so as to bond the second set of components to the second panel, wherein the second set of components are compressed against the second panel at the same time that the first set of components are compressed against the first panel.
For example in one of the embodiments described below the first set of components are stringers etc. associated with an upper surface of a wing-box, and the second set are stringers etc. associated with a lower surface of a wing-box.
A further aspect of the invention provides a tool set comprising:
at least two inner mould line tools;
at least two outer mould line tools; and one or more spacers, each adapted to be removably fitted between the inner mould line tools so as to maintain a desired spacing between the inner mould line tools.
Such a tool set can be used in a method of manufacturing a part, the method comprising:
arranging a first set of components on an outer face of a first inner mould line tool;
arranging a second set of components on an outer face of a second inner mould line tool;
fitting one or more spacers between the inner mould line tools, with the spacer(s) engaging inner faces of the inner mould line tools so as to maintain a desired spacing between the inner mould line tools;
forming a layer around the inner mould line tools;
fitting outer mould line tools on opposite sides of the inner mould line tools;
moulding the part by compressing the layer and the components between the inner and outer mould line tools;
removing the spacer(s);
disengaging the inner mould line tools from the part after the spacer(s) have been removed; and removing the inner mould line tools from the part.
This method enables the inner mould line tools to be removed easily from the composite part after formation of the part. Typically the part is a tubular part such as a full wing-box.
A further aspect of the invention provides a method of manufacturing a part, the method comprising:
arranging a set of components on one or more inner mould line tools;
forming a layer around the inner mould line tool(s);
fitting a pair of outer mould line tools on opposite sides of the inner mould line tool(s);
moulding the part by compressing the layer and the components between the inner and outer mould line tools; and removing the inner mould line tool(s) from the part.
Typically the layer is formed by wrapping around the or each inner mould line tool.
Typically the or each inner mould line tool is rotated as the layer is wrapped around the inner mould line tool(s), for instance by a filament winding machine.
The various aspects of the invention may be used to form an aircraft part such as a full or half wing-box, or may be used in a variety of non-aircraft applications. The part is typically, although not exclusively, formed from a composite material.
BRIEF DESCRIPTION OF THE DRAWINGS
Embodiments of the invention will now be described with reference to the accompanying drawings, in which:
FIG. 1 shows an Inner Mould Line (IML) tool for a half wing-box part;
FIG. 2a shows a first back-to-back mould tool;
FIG. 2b shows a second back-to-back mould tool;
FIG. 3 shows the IML tool with the preforms and mandrels fitted;
FIG. 4 shows a curing assembly for the half wing-box part;
FIG. 5 shows an Inner Mould Line (IML) tool for a full wing-box part;
FIG. 6 is a sectional view through a curing assembly for the full wing-box part;
FIG. 7 shows the upper and lower Outer Mould Line (OML) used in the assembly of Figure 6;
FIG. 8 is a side view of a Main Landing Gear (MLG) IML tool used in the assembly of Figure 6;
FIG. 9 is a side view of a Pylon IML tool used in the assembly of Figure 6;
FIG. 10 is a cross-sectional view showing one of the interfaces between the MLG IML tool and the wing-box IML tool in the assembly of Figure 6;
FIGs 11-18 show the production of a half wing-box part; and FIGs 19-22 show the production of a full wing-box part.
DETAILED DESCRIPTION OF EMBODIMENT(S) Figures 1 to 4 illustrate a process for manufacturing a half wing-box composite part.
An inner mould line (IML) tool 1 shown in Figure 1 comprises a contiguous piece of steel machined from a billet with an upper face defining an upper moulding surface.
A pylon pad-up recess 2 and a landing gear pad-up recess 4 are machined in the leading and trailing edges of the upper moulding surface. Material is then removed from the upper moulding surface by machining to form a number of mandrel recesses. The mandrel recesses include spar channels 5 running spanwise along the leading and trailing edges of the tool, four stringer channels 6 running spanwise along the tool, and three rib foot channels 8 running chordwise across the tool. The stringer channels 6 and rib foot channels 8 each have a base and a pair of opposite side walls, whereas the spar channels, being formed at the edge of the upper moulding surface, have a base and only a single side wall. Mandrel locating holes are provided in the base of each mandrel recess. One of such holes 9 is partially visible in Figure 1. The upper moulding surface is divided by the mandrel recesses into an array of islands 3. Tool locating holes 7 are provided at the root end of the tool 1.
A flexible surface covering (such as a laminate of pre-cured plies) may be bonded or bolted to the upper moulding surface before the mandrel recesses have been formed.
The flexible surface covering can then be machined to form a desired moulding profile, and punched through to form the tool and mandrel locating holes.
A stringer mould tool 10 is shown in Figure 2a. The tool comprises a pair of mandrels 11,12 arranged back-to-back. The mandrels 11,12 are similar in form and so only mandrel 11 will be described in detail. A stringer half is formed on the mandrel by laying a laminate charge (such as a prepreg) on the mandrel, and moulding the charge against two faces 15,16 of the mandrel. This may be achieved by a variety of manufacturing techniques. For example a flexible diaphragm may be laid over the charge, and one side of the diaphragm evacuated to mould the charge using hydrostatic pressure (in combination with heat). This results in an L-shaped stringer half, which is laid back to back with another stringer half formed over mandrel 12. A row of stringer preforms 30, each formed from a pair of stringer halves, is shown in Figure 3.
The mandrels have location pins 13,14 which fit into the mandrel locator holes 9 in the base of the stringer recesses 6 to accurately locate the stringer mould tool.
Although the male/female connection is provided in this case by male parts on the mandrels, and female holes in the mandrel recesses, in an alternative embodiment the male parts may be provided instead in the mandrel recesses.
A trailing edge spar-cap mandrel 34, shown in Figure 3, is used to mould a trailing edge spar-cap preform 33 in a similar manner to the stringers 30. That is, a charge (such as a prepreg) is placed on the mandrel 34, and moulded the against two faces of the mandrel, for instance by vacuum forming. A leading edge spar-cap preform 31 is formed in a similar manner on a spar-cap mandrel 32.
Back-to-back rib foot tools (not shown), similar to the stringer tool 10, are used to mould T-shaped rib foot preforms 36 shown in Figure 3.
An assembly line arrangement may be used to simultaneously manufacture the preforms, thus maximising the production rate.
After the spar-cap, stringer and rib foot preforms have been formed, they are transported to the IML tool 1 on their respective mandrels, and the mandrels are fitted into their respective channels in the tool as shown in Figure 3. The preforms may be cured or uncured prior to being fitted onto the tool 1.
Note that the two-sided channels (that is the stringer channels 6 and the rib foot channels 8) receive their respective mandrel as a push fit to accurately locate the mandrel.
Figure 4 shows a curing assembly including the IML tool 1 and an outer mould line (OML) tool 40. The OML tool 40 is located horizontally on a curing jig (not shown) using locating holes (not shown) in the tool. A skin 41 is laid onto the OML tool 40. The skin 41 may be laid up by hand or using a tape laying machine, with prepreg or woven fabric.
The IML tool 1 (with the preforms and mandrels in place as shown in Figure 3) is inverted and placed on top of the skin to form the assembly shown in Figure 4. Dowel pins 42 extending from the OML tool 40 fit into the locating holes 7 (see Figure 1) in the IML tool 1 in order to accurately locate the IML and OML tools relative to each other.
The assembly of Figure 4 is then sealed and encapsulated between a pair of flexible diaphragms. A vacuum is applied between the diaphragms to compress the IML and OML
tools together, and heat and pressure are applied in an autoclave to cure the components and bond them together.
During cure, the skin 41 has a number of portions which engage with (and are compressed against) the islands 3 in the IML tool 1 and are thus moulded (on their inner face) to conform to the shape of the islands 3. Other portions of the skin engage with (and are compressed against) the stringers 30, rib feet 36, and spar caps 31,33 so as to bond them together. The components 30,36,31,33 are compressed and moulded on their other side by their respective mandrels.
The resulting half-wing part is then removed from the mould tools, and manholes and any other critical areas are machined to provide a part ready for assembly. In the final assembly of the wing box, the rib feet 36 are bolted to rib webs (not shown) and the spar-caps 31,33 are bolted to spar webs (not shown). The rib webs and spar webs are bolted in turn to another similar half-wing part (also not shown). Some additional bolting of the spar caps may be required in areas of high shear.
The IML tool 1 can be used as part of a modular tool set containing a number of different mandrels, each configured to fit into a mandrel recess and form a respective composite component. Thus for example the stringer mould tools 10 may be removed from the stringer mandrel channels 6 and substituted with alternative stringer mould tools which, whilst being shaped and sized to be received as a push fit into the channels 6, are configured to form a stringer of a different shape or size. Thus for example a stringer mould tool 10' shown in Figure 2b may be used to form an I-shaped stringer 30' (instead of the T-shaped stringer 30 formed by the tool 10) in a subsequent co-curing/bonding process with a different skin The same modular approach can be employed for the spar caps and rib feet. This enables the same IML tool 1 to be used to form a number of different parts which each have a common general shape (as defined by the islands 3 which form the upper moulding surface) but have different components. This reduces the part count, thus minimising manufacturing costs.
The IML tool 1 has stringer mandrel recesses 5, and additional mandrel recesses each configured to receive a mandrel for an additional component (in this case, spar caps and rib feet). This integrated tooling approach saves on manufacturing time since it enables the stringers, spar caps and rib feet to be simultaneously bonded to the skin.
Figures 5 to 11 illustrate a process for manufacturing a full wing-box composite part.
An inner mould line (IML) tool 50 shown in Figure 5 comprises a contiguous piece of steel with an upper face defining an upper moulding surface, a lower face (opposite to the upper face) defining a lower moulding surface, and leading and trailing faces (adjacent to the upper and lower faces) defining leading and trailing moulding surfaces. A
pylon pad-up recess 53 and a landing gear pad-up recess 52 are formed in the leading and trailing edges of the upper moulding surface. The moulding surfaces are then machined to form two pairs of upper and lower spar channels 55, upper and lower stringer channels 54 running spanwise along the tool, and upper and lower rib foot channels 51 running chordwise across the tool. Only the upper rib foot channels 51 are shown in Figure 5, but similar rib channels are formed in the hidden lower moulding surface. Islands 58 are located between the channels. Rib post recesses 57 are formed in the leading and trailing moulding surfaces in line with the rib foot channels 51. Only two rib post recesses 57 are shown in Figure 5, but a third rib post recess may be provided in line with the rib foot channel 51 at the far end of the tool. Flats are formed in the lower moulding surface in the desired positions of manholes in the finished wing box. Only a single flat 56 at the root end of the IML tool is shown in Figure 5, but a number of such flats are positioned along the length of the hidden lower moulding surface.
A flexible surface covering (such as a laminate of pre-cured plies) may be wrapped around the tool 50 (and then bonded or bolted in place) before the mandrel recesses have been formed. The flexible surface covering can then be machined to form a desired moulding profile.
Stringers, rib feet and spar caps are formed in a similar manner to the stringers, rib feet and spar caps shown in Figure 3, and fitted in place in their respective recesses on the IML tool 50. Rib posts (not shown) are also moulded onto back-to-back tools similar to the tool stringer tool 10 shown in Figure 3, and the tools are fitted into the rib post recesses 57.
A set of four support struts 49 is shown in Figure 6. A series of such sets of support struts 49 are mounted at intervals on a shaft 69 which runs along the centre line of the tool 50, with the ends of the struts 49 engaging the inner corners of the tool. The shaft 69 is rotated, and a capping layer 58 is wound onto the IML tool 50 by a filament winding machine as it rotates. The capping layer 58 comprises a series of capping plies. The fibres in most of the capping plies are likely to run at an angle of approximately 900 to the spanwise direction of the tool (that is, the axis of rotation of the tool).
However, angles of up to 450 may be achieved by moving the spool of the filament winding machine at an angle to the shaft as the spool unwinds.
Figure 6 shows a curing assembly including the IML tool 50, an upper cover OML
tool 53, a lower cover OML tool 54, a Main Landing Gear (MLG) IML tool 51, and a Pylon IML
tool 52.
The lower cover OML tool 54 is located horizontally on a curing jig (not shown) with pins of the tooling jig passing through locating holes 56 (shown in Figure 7) in the tool 54. A
lower skin 57 is laid onto the lower cover OML tool 54. The IML tool 50 (with the preforms and mandrels in place as shown in Figure 6) is placed on top of the skin 57 as shown in Figure 6, with the pins of the tooling jig passing through holes (not shown) in the IML tool 50 to accurately locate the IML and OML tools relative to each other.
The MLG IML tool 51 and Pylon IML tool 52 are then positioned in place as shown in Figure 6.
The MLG IML tool 51 is shown in detail in Figure 8. The tool 51 is symmetrical about its centre line, so only the upper half will be described in detail. The upper half comprises an upper caul plate with an upper face 60 which engages the upper skin 59 and a side face 64 which engages the capping layer 58. The side face 64 extends into a flange with a pilot hole 61. A pin 62 has a nut 63 threaded onto its distal end (not shown).
The nut 63 engages the nut carried by the lower caul plate, and one or both of the nuts can be rotated to adjust the spacing between the caul plates, thus ensuring accurate thickness for the upper and lower skins 57,59.
An interface between the MLG IML tool 51 and the IML tool 50 is shown in Figure 10.
The tool 51 may extend along the length of the tool 50, or may be located in line with the landing gear pad-up recess 52. The tool 50 has a pilot hole 65 aligned with the pilot hole 61 in the tool 51. A pilot hole 66 is punched through the capping layer 68 in line with the pilot holes 61,65. A bolt 80 is passed through the pilot holes 61,65,66 and held in place by nuts 82, 83. A cylindrical collar 81 is fitted onto the bolt 80 and engages the opposed faces of the tools 50,51. The length of the collar 81 is carefully controlled to accurately set the spacing between the tools, and thus the thickness of the capping layer 58.
The Pylon IML tool 52 is shown in detail in Figure 9. It has a similar construction to the tool 51 so will not be described in detail. Similar bolt interfaces are provided between the tool 52 and the IML tool 50.
The tools 50,51,52 are then secured, removed from the jig, and rotated by 180 .
The upper cover OML tool 53 is located horizontally on the curing jig using the pins on the curing jig passing through locating holes 56 in the tool 53. An upper skin 59 is laid onto the upper cover OML tool 53. The tools 50,51,52 are then placed on top of the skin 59, with the pins of the tooling jig passing through holes (not shown) in the IML
tool 50 to accurately locate the IML and OML tools relative to each other.
The assembly of Figure 6 is then secured, sealed and bagged for curing in an autoclave.
The IML tool 50 (in common with the IML tool 1) can be used as part of a modular tool set containing a number of different mandrels, each configured to fit into a mandrel recess and form a respective composite component.
The IML tool 50 has stringer mandrel recesses, and additional mandrel recesses each configured to receive a mandrel for an additional component (in this case, spar caps, rib posts and rib feet). This integrated tooling approach saves on manufacturing time since it enables the stringers, spar caps, rib posts and rib feet to be simultaneously bonded. Also, the full wing-box IML tool enables the upper and lower skins to be bonded to their respective components at the same time, reducing assembly time and cost compared with the half wing-box version. Also, there is no additional assembly step required to bolt the spar caps to a spar web- the spar web being provided by the capping layer 58.
However the half-wing box version, producing a smaller part, enables non-destructive testing to be performed more easily on the part.
The OML tools are then removed, and the IML tools removed from the larger root end of the full wing-box part. Manholes and any other critical areas are then machined to provide a part ready for assembly. During assembly, rib webs are passed through the root end of the wing-box and bolted to the rib posts and rib feet. Some additional bolting of the spar caps to the skins 57,59 may be required in areas of high shear.
Figures 11-16 illustrate an alternative process for manufacturing a half wing-box composite part. The process is similar to the process shown in Figures 1-4, and only the differences will be described in detail. An IML tool 100 shown in Figure 13 is formed from a billet 101 shown in Figure 11 which is first machined to form the inner mould line surface, spar channels and pad-up recesses as shown in Figure 12, and then machined to form the stringer and rib foot recesses as shown in Figure 13. The tool 100 receives the same mandrels as the tool 1, and these are shown individually in Figure 13 prior to insertion into their respective mandrel recesses. Figure 14 shows the mandrels and preforms in place, and Figure 15 shows a capping layer 102 which is then draped onto the tool.
Caul plates 103 ,104 are then fitted to the leading and trailing edges as shown in Figure 16.
As shown in Figure 17, a skin 105 is laid onto an OML tool 106. The tool 100 is placed onto the skin 105 as shown in Figure 18, and dowel pins extending from a plate 111 are inserted into holes in the OML tool and caul plates to accurately position the parts. Four of the dowel pins 107-110 are shown in Figure 18, the other dowel pins being hidden. The assembly of Figure 18 is then bagged, and cured in an autoclave.
Figures 19-22 illustrate an alternative process for manufacturing a full wing-box composite part. A pair of IML tools 120,121 similar to the IML tool 100 are fitted with preforms as shown in Figure 21. Four intercostal spacer plates 122, shown in Figure 19, are removably fitted between the IML tools 121,120. The upper and lower faces of the spacer plates engage the inner faces of the inner mould line tools so as to maintain a desired spacing between them. A capping layer 123 is then wound onto the assembly as shown in Figure 21. In contrast with the assembly of Figure 6 in which the assembly is rotated on a shaft which runs along the centre line of the tool, the assembly of Figure 21 can be rotated by the spacer plates 122.
After the capping layer 123 has been formed, caul plates 124,125 shown in Figure 20 are fitted as shown in Figure 22. Upper and lower OML tools 126,127 (both carrying skins, not labelled) are then fitted as shown in Figure 22. The assembly of Figure 22 is then bagged, and cured in an autoclave.
After curing, the OML tools 126,127 and caul plates 124,125 are removed. The four intercostal spacer plates 122 can then be removed from the root and tip end of the wing box, or from the leading and trailing edges. This then enables the IML tools 120,121 to be disengaged from the cured wing box (by moving the upper tool 121 down, and moving the lower tool 120 up) and removed from the root end or the tip end.
Although the invention has been described above with reference to one or more preferred embodiments, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.
forming a component on a mandrel;
fitting the mandrel into a mandrel recess of a moulding tool;
arranging a panel with a first portion of the panel engaging a moulding surface of the moulding tool and a second portion of the panel engaging the component on the mandrel;
bonding the first portion of the panel to the component by compressing them against the first mandrel; and moulding the second portion of the panel by compressing it against the moulding surface of the moulding tool.
The panel may be a variety of elements, depending on the application. In the preferred embodiments described below, the panel is either a wing skin or part of a capping layer which is wrapped around the moulding tool.
A further aspect of the invention provides a method of manufacturing first and second parts, the method comprising:
manufacturing the first part by:
arranging a first component on a first mandrel;
fitting the first mandrel into a mandrel recess of a moulding tool;
arranging a first panel with a first portion of the panel engaging a moulding surface of the moulding tool and a second portion of the panel engaging the first component on the first mandrel;
bonding the first portion of the panel to the first component by compressing them against the first mandrel; and 21849951.2 3 moulding the second portion of the panel by compressing it against the moulding surface of the moulding tool;
removing the first mandrel from the mandrel recess; and manufacturing the second part by:
arranging a second component on the second mandrel;
fitting the second mandrel into the mandrel recess of the moulding tool;
arranging a second panel with a first portion of the panel engaging the moulding surface of the moulding tool and a second portion of the panel engaging the second component on the second mandrel;
bonding the first portion of the panel to the second component by compressing them against the second mandrel; and moulding the second portion of the panel by compressing it against the moulding surface of the moulding tool.
A further aspect of the invention provides a method of manufacturing a part, the method comprising:
arranging a set of components on a moulding tool; and simultaneously compressing the set of components on the moulding tool against a panel so as to bond the components to the panel, wherein the set of components includes a plurality of stringers, and one or more additional components.
In one embodiment of the invention, the method further comprises:
arranging a second set of components on the moulding tool; and compressing the second set of components on the moulding tool against a second panel so as to bond the second set of components to the second panel, wherein the second set of components are compressed against the second panel at the same time that the first set of components are compressed against the first panel.
For example in one of the embodiments described below the first set of components are stringers etc. associated with an upper surface of a wing-box, and the second set are stringers etc. associated with a lower surface of a wing-box.
A further aspect of the invention provides a tool set comprising:
at least two inner mould line tools;
at least two outer mould line tools; and one or more spacers, each adapted to be removably fitted between the inner mould line tools so as to maintain a desired spacing between the inner mould line tools.
Such a tool set can be used in a method of manufacturing a part, the method comprising:
arranging a first set of components on an outer face of a first inner mould line tool;
arranging a second set of components on an outer face of a second inner mould line tool;
fitting one or more spacers between the inner mould line tools, with the spacer(s) engaging inner faces of the inner mould line tools so as to maintain a desired spacing between the inner mould line tools;
forming a layer around the inner mould line tools;
fitting outer mould line tools on opposite sides of the inner mould line tools;
moulding the part by compressing the layer and the components between the inner and outer mould line tools;
removing the spacer(s);
disengaging the inner mould line tools from the part after the spacer(s) have been removed; and removing the inner mould line tools from the part.
This method enables the inner mould line tools to be removed easily from the composite part after formation of the part. Typically the part is a tubular part such as a full wing-box.
A further aspect of the invention provides a method of manufacturing a part, the method comprising:
arranging a set of components on one or more inner mould line tools;
forming a layer around the inner mould line tool(s);
fitting a pair of outer mould line tools on opposite sides of the inner mould line tool(s);
moulding the part by compressing the layer and the components between the inner and outer mould line tools; and removing the inner mould line tool(s) from the part.
Typically the layer is formed by wrapping around the or each inner mould line tool.
Typically the or each inner mould line tool is rotated as the layer is wrapped around the inner mould line tool(s), for instance by a filament winding machine.
The various aspects of the invention may be used to form an aircraft part such as a full or half wing-box, or may be used in a variety of non-aircraft applications. The part is typically, although not exclusively, formed from a composite material.
BRIEF DESCRIPTION OF THE DRAWINGS
Embodiments of the invention will now be described with reference to the accompanying drawings, in which:
FIG. 1 shows an Inner Mould Line (IML) tool for a half wing-box part;
FIG. 2a shows a first back-to-back mould tool;
FIG. 2b shows a second back-to-back mould tool;
FIG. 3 shows the IML tool with the preforms and mandrels fitted;
FIG. 4 shows a curing assembly for the half wing-box part;
FIG. 5 shows an Inner Mould Line (IML) tool for a full wing-box part;
FIG. 6 is a sectional view through a curing assembly for the full wing-box part;
FIG. 7 shows the upper and lower Outer Mould Line (OML) used in the assembly of Figure 6;
FIG. 8 is a side view of a Main Landing Gear (MLG) IML tool used in the assembly of Figure 6;
FIG. 9 is a side view of a Pylon IML tool used in the assembly of Figure 6;
FIG. 10 is a cross-sectional view showing one of the interfaces between the MLG IML tool and the wing-box IML tool in the assembly of Figure 6;
FIGs 11-18 show the production of a half wing-box part; and FIGs 19-22 show the production of a full wing-box part.
DETAILED DESCRIPTION OF EMBODIMENT(S) Figures 1 to 4 illustrate a process for manufacturing a half wing-box composite part.
An inner mould line (IML) tool 1 shown in Figure 1 comprises a contiguous piece of steel machined from a billet with an upper face defining an upper moulding surface.
A pylon pad-up recess 2 and a landing gear pad-up recess 4 are machined in the leading and trailing edges of the upper moulding surface. Material is then removed from the upper moulding surface by machining to form a number of mandrel recesses. The mandrel recesses include spar channels 5 running spanwise along the leading and trailing edges of the tool, four stringer channels 6 running spanwise along the tool, and three rib foot channels 8 running chordwise across the tool. The stringer channels 6 and rib foot channels 8 each have a base and a pair of opposite side walls, whereas the spar channels, being formed at the edge of the upper moulding surface, have a base and only a single side wall. Mandrel locating holes are provided in the base of each mandrel recess. One of such holes 9 is partially visible in Figure 1. The upper moulding surface is divided by the mandrel recesses into an array of islands 3. Tool locating holes 7 are provided at the root end of the tool 1.
A flexible surface covering (such as a laminate of pre-cured plies) may be bonded or bolted to the upper moulding surface before the mandrel recesses have been formed.
The flexible surface covering can then be machined to form a desired moulding profile, and punched through to form the tool and mandrel locating holes.
A stringer mould tool 10 is shown in Figure 2a. The tool comprises a pair of mandrels 11,12 arranged back-to-back. The mandrels 11,12 are similar in form and so only mandrel 11 will be described in detail. A stringer half is formed on the mandrel by laying a laminate charge (such as a prepreg) on the mandrel, and moulding the charge against two faces 15,16 of the mandrel. This may be achieved by a variety of manufacturing techniques. For example a flexible diaphragm may be laid over the charge, and one side of the diaphragm evacuated to mould the charge using hydrostatic pressure (in combination with heat). This results in an L-shaped stringer half, which is laid back to back with another stringer half formed over mandrel 12. A row of stringer preforms 30, each formed from a pair of stringer halves, is shown in Figure 3.
The mandrels have location pins 13,14 which fit into the mandrel locator holes 9 in the base of the stringer recesses 6 to accurately locate the stringer mould tool.
Although the male/female connection is provided in this case by male parts on the mandrels, and female holes in the mandrel recesses, in an alternative embodiment the male parts may be provided instead in the mandrel recesses.
A trailing edge spar-cap mandrel 34, shown in Figure 3, is used to mould a trailing edge spar-cap preform 33 in a similar manner to the stringers 30. That is, a charge (such as a prepreg) is placed on the mandrel 34, and moulded the against two faces of the mandrel, for instance by vacuum forming. A leading edge spar-cap preform 31 is formed in a similar manner on a spar-cap mandrel 32.
Back-to-back rib foot tools (not shown), similar to the stringer tool 10, are used to mould T-shaped rib foot preforms 36 shown in Figure 3.
An assembly line arrangement may be used to simultaneously manufacture the preforms, thus maximising the production rate.
After the spar-cap, stringer and rib foot preforms have been formed, they are transported to the IML tool 1 on their respective mandrels, and the mandrels are fitted into their respective channels in the tool as shown in Figure 3. The preforms may be cured or uncured prior to being fitted onto the tool 1.
Note that the two-sided channels (that is the stringer channels 6 and the rib foot channels 8) receive their respective mandrel as a push fit to accurately locate the mandrel.
Figure 4 shows a curing assembly including the IML tool 1 and an outer mould line (OML) tool 40. The OML tool 40 is located horizontally on a curing jig (not shown) using locating holes (not shown) in the tool. A skin 41 is laid onto the OML tool 40. The skin 41 may be laid up by hand or using a tape laying machine, with prepreg or woven fabric.
The IML tool 1 (with the preforms and mandrels in place as shown in Figure 3) is inverted and placed on top of the skin to form the assembly shown in Figure 4. Dowel pins 42 extending from the OML tool 40 fit into the locating holes 7 (see Figure 1) in the IML tool 1 in order to accurately locate the IML and OML tools relative to each other.
The assembly of Figure 4 is then sealed and encapsulated between a pair of flexible diaphragms. A vacuum is applied between the diaphragms to compress the IML and OML
tools together, and heat and pressure are applied in an autoclave to cure the components and bond them together.
During cure, the skin 41 has a number of portions which engage with (and are compressed against) the islands 3 in the IML tool 1 and are thus moulded (on their inner face) to conform to the shape of the islands 3. Other portions of the skin engage with (and are compressed against) the stringers 30, rib feet 36, and spar caps 31,33 so as to bond them together. The components 30,36,31,33 are compressed and moulded on their other side by their respective mandrels.
The resulting half-wing part is then removed from the mould tools, and manholes and any other critical areas are machined to provide a part ready for assembly. In the final assembly of the wing box, the rib feet 36 are bolted to rib webs (not shown) and the spar-caps 31,33 are bolted to spar webs (not shown). The rib webs and spar webs are bolted in turn to another similar half-wing part (also not shown). Some additional bolting of the spar caps may be required in areas of high shear.
The IML tool 1 can be used as part of a modular tool set containing a number of different mandrels, each configured to fit into a mandrel recess and form a respective composite component. Thus for example the stringer mould tools 10 may be removed from the stringer mandrel channels 6 and substituted with alternative stringer mould tools which, whilst being shaped and sized to be received as a push fit into the channels 6, are configured to form a stringer of a different shape or size. Thus for example a stringer mould tool 10' shown in Figure 2b may be used to form an I-shaped stringer 30' (instead of the T-shaped stringer 30 formed by the tool 10) in a subsequent co-curing/bonding process with a different skin The same modular approach can be employed for the spar caps and rib feet. This enables the same IML tool 1 to be used to form a number of different parts which each have a common general shape (as defined by the islands 3 which form the upper moulding surface) but have different components. This reduces the part count, thus minimising manufacturing costs.
The IML tool 1 has stringer mandrel recesses 5, and additional mandrel recesses each configured to receive a mandrel for an additional component (in this case, spar caps and rib feet). This integrated tooling approach saves on manufacturing time since it enables the stringers, spar caps and rib feet to be simultaneously bonded to the skin.
Figures 5 to 11 illustrate a process for manufacturing a full wing-box composite part.
An inner mould line (IML) tool 50 shown in Figure 5 comprises a contiguous piece of steel with an upper face defining an upper moulding surface, a lower face (opposite to the upper face) defining a lower moulding surface, and leading and trailing faces (adjacent to the upper and lower faces) defining leading and trailing moulding surfaces. A
pylon pad-up recess 53 and a landing gear pad-up recess 52 are formed in the leading and trailing edges of the upper moulding surface. The moulding surfaces are then machined to form two pairs of upper and lower spar channels 55, upper and lower stringer channels 54 running spanwise along the tool, and upper and lower rib foot channels 51 running chordwise across the tool. Only the upper rib foot channels 51 are shown in Figure 5, but similar rib channels are formed in the hidden lower moulding surface. Islands 58 are located between the channels. Rib post recesses 57 are formed in the leading and trailing moulding surfaces in line with the rib foot channels 51. Only two rib post recesses 57 are shown in Figure 5, but a third rib post recess may be provided in line with the rib foot channel 51 at the far end of the tool. Flats are formed in the lower moulding surface in the desired positions of manholes in the finished wing box. Only a single flat 56 at the root end of the IML tool is shown in Figure 5, but a number of such flats are positioned along the length of the hidden lower moulding surface.
A flexible surface covering (such as a laminate of pre-cured plies) may be wrapped around the tool 50 (and then bonded or bolted in place) before the mandrel recesses have been formed. The flexible surface covering can then be machined to form a desired moulding profile.
Stringers, rib feet and spar caps are formed in a similar manner to the stringers, rib feet and spar caps shown in Figure 3, and fitted in place in their respective recesses on the IML tool 50. Rib posts (not shown) are also moulded onto back-to-back tools similar to the tool stringer tool 10 shown in Figure 3, and the tools are fitted into the rib post recesses 57.
A set of four support struts 49 is shown in Figure 6. A series of such sets of support struts 49 are mounted at intervals on a shaft 69 which runs along the centre line of the tool 50, with the ends of the struts 49 engaging the inner corners of the tool. The shaft 69 is rotated, and a capping layer 58 is wound onto the IML tool 50 by a filament winding machine as it rotates. The capping layer 58 comprises a series of capping plies. The fibres in most of the capping plies are likely to run at an angle of approximately 900 to the spanwise direction of the tool (that is, the axis of rotation of the tool).
However, angles of up to 450 may be achieved by moving the spool of the filament winding machine at an angle to the shaft as the spool unwinds.
Figure 6 shows a curing assembly including the IML tool 50, an upper cover OML
tool 53, a lower cover OML tool 54, a Main Landing Gear (MLG) IML tool 51, and a Pylon IML
tool 52.
The lower cover OML tool 54 is located horizontally on a curing jig (not shown) with pins of the tooling jig passing through locating holes 56 (shown in Figure 7) in the tool 54. A
lower skin 57 is laid onto the lower cover OML tool 54. The IML tool 50 (with the preforms and mandrels in place as shown in Figure 6) is placed on top of the skin 57 as shown in Figure 6, with the pins of the tooling jig passing through holes (not shown) in the IML tool 50 to accurately locate the IML and OML tools relative to each other.
The MLG IML tool 51 and Pylon IML tool 52 are then positioned in place as shown in Figure 6.
The MLG IML tool 51 is shown in detail in Figure 8. The tool 51 is symmetrical about its centre line, so only the upper half will be described in detail. The upper half comprises an upper caul plate with an upper face 60 which engages the upper skin 59 and a side face 64 which engages the capping layer 58. The side face 64 extends into a flange with a pilot hole 61. A pin 62 has a nut 63 threaded onto its distal end (not shown).
The nut 63 engages the nut carried by the lower caul plate, and one or both of the nuts can be rotated to adjust the spacing between the caul plates, thus ensuring accurate thickness for the upper and lower skins 57,59.
An interface between the MLG IML tool 51 and the IML tool 50 is shown in Figure 10.
The tool 51 may extend along the length of the tool 50, or may be located in line with the landing gear pad-up recess 52. The tool 50 has a pilot hole 65 aligned with the pilot hole 61 in the tool 51. A pilot hole 66 is punched through the capping layer 68 in line with the pilot holes 61,65. A bolt 80 is passed through the pilot holes 61,65,66 and held in place by nuts 82, 83. A cylindrical collar 81 is fitted onto the bolt 80 and engages the opposed faces of the tools 50,51. The length of the collar 81 is carefully controlled to accurately set the spacing between the tools, and thus the thickness of the capping layer 58.
The Pylon IML tool 52 is shown in detail in Figure 9. It has a similar construction to the tool 51 so will not be described in detail. Similar bolt interfaces are provided between the tool 52 and the IML tool 50.
The tools 50,51,52 are then secured, removed from the jig, and rotated by 180 .
The upper cover OML tool 53 is located horizontally on the curing jig using the pins on the curing jig passing through locating holes 56 in the tool 53. An upper skin 59 is laid onto the upper cover OML tool 53. The tools 50,51,52 are then placed on top of the skin 59, with the pins of the tooling jig passing through holes (not shown) in the IML
tool 50 to accurately locate the IML and OML tools relative to each other.
The assembly of Figure 6 is then secured, sealed and bagged for curing in an autoclave.
The IML tool 50 (in common with the IML tool 1) can be used as part of a modular tool set containing a number of different mandrels, each configured to fit into a mandrel recess and form a respective composite component.
The IML tool 50 has stringer mandrel recesses, and additional mandrel recesses each configured to receive a mandrel for an additional component (in this case, spar caps, rib posts and rib feet). This integrated tooling approach saves on manufacturing time since it enables the stringers, spar caps, rib posts and rib feet to be simultaneously bonded. Also, the full wing-box IML tool enables the upper and lower skins to be bonded to their respective components at the same time, reducing assembly time and cost compared with the half wing-box version. Also, there is no additional assembly step required to bolt the spar caps to a spar web- the spar web being provided by the capping layer 58.
However the half-wing box version, producing a smaller part, enables non-destructive testing to be performed more easily on the part.
The OML tools are then removed, and the IML tools removed from the larger root end of the full wing-box part. Manholes and any other critical areas are then machined to provide a part ready for assembly. During assembly, rib webs are passed through the root end of the wing-box and bolted to the rib posts and rib feet. Some additional bolting of the spar caps to the skins 57,59 may be required in areas of high shear.
Figures 11-16 illustrate an alternative process for manufacturing a half wing-box composite part. The process is similar to the process shown in Figures 1-4, and only the differences will be described in detail. An IML tool 100 shown in Figure 13 is formed from a billet 101 shown in Figure 11 which is first machined to form the inner mould line surface, spar channels and pad-up recesses as shown in Figure 12, and then machined to form the stringer and rib foot recesses as shown in Figure 13. The tool 100 receives the same mandrels as the tool 1, and these are shown individually in Figure 13 prior to insertion into their respective mandrel recesses. Figure 14 shows the mandrels and preforms in place, and Figure 15 shows a capping layer 102 which is then draped onto the tool.
Caul plates 103 ,104 are then fitted to the leading and trailing edges as shown in Figure 16.
As shown in Figure 17, a skin 105 is laid onto an OML tool 106. The tool 100 is placed onto the skin 105 as shown in Figure 18, and dowel pins extending from a plate 111 are inserted into holes in the OML tool and caul plates to accurately position the parts. Four of the dowel pins 107-110 are shown in Figure 18, the other dowel pins being hidden. The assembly of Figure 18 is then bagged, and cured in an autoclave.
Figures 19-22 illustrate an alternative process for manufacturing a full wing-box composite part. A pair of IML tools 120,121 similar to the IML tool 100 are fitted with preforms as shown in Figure 21. Four intercostal spacer plates 122, shown in Figure 19, are removably fitted between the IML tools 121,120. The upper and lower faces of the spacer plates engage the inner faces of the inner mould line tools so as to maintain a desired spacing between them. A capping layer 123 is then wound onto the assembly as shown in Figure 21. In contrast with the assembly of Figure 6 in which the assembly is rotated on a shaft which runs along the centre line of the tool, the assembly of Figure 21 can be rotated by the spacer plates 122.
After the capping layer 123 has been formed, caul plates 124,125 shown in Figure 20 are fitted as shown in Figure 22. Upper and lower OML tools 126,127 (both carrying skins, not labelled) are then fitted as shown in Figure 22. The assembly of Figure 22 is then bagged, and cured in an autoclave.
After curing, the OML tools 126,127 and caul plates 124,125 are removed. The four intercostal spacer plates 122 can then be removed from the root and tip end of the wing box, or from the leading and trailing edges. This then enables the IML tools 120,121 to be disengaged from the cured wing box (by moving the upper tool 121 down, and moving the lower tool 120 up) and removed from the root end or the tip end.
Although the invention has been described above with reference to one or more preferred embodiments, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.
Claims (5)
1. A method of manufacturing a wingbox, the method comprising:
arranging a first set of components in a first set of recesses on an outer face of a first inner mould line tool, the inner mould line tool having an inner face;
arranging a second set of components in a second set of recesses on an outer face of a second inner mould line tool, the second inner mould line tool having an inner face;
fitting one or more spacers between the inner mould line tools. with the spacer(s) engaging inner faces of the inner mould line tools so as to maintain a desired spacing between the inner mould line tools, wherein each spacer has an upper face and a lower face opposite to the upper face, and each spacer is fitted with the upper and lower faces of the spacer engaging the inner faces of the inner mould line tools;
forming a layer around the inner mould line tools and forming a tubular part.
said part having first and second open ends;
fitting outer mould line Lois on opposite sides of the inner mould line tools;
moulding the part by compressing the layer and the components between the inner and outer mould line tools;
removing the at least one spacer(s);
disengaging the inner mould line tools from the part after the at least one spacer(s) have been removed; and removing the inner mould line tools from the part through the at least one of the open ends.
arranging a first set of components in a first set of recesses on an outer face of a first inner mould line tool, the inner mould line tool having an inner face;
arranging a second set of components in a second set of recesses on an outer face of a second inner mould line tool, the second inner mould line tool having an inner face;
fitting one or more spacers between the inner mould line tools. with the spacer(s) engaging inner faces of the inner mould line tools so as to maintain a desired spacing between the inner mould line tools, wherein each spacer has an upper face and a lower face opposite to the upper face, and each spacer is fitted with the upper and lower faces of the spacer engaging the inner faces of the inner mould line tools;
forming a layer around the inner mould line tools and forming a tubular part.
said part having first and second open ends;
fitting outer mould line Lois on opposite sides of the inner mould line tools;
moulding the part by compressing the layer and the components between the inner and outer mould line tools;
removing the at least one spacer(s);
disengaging the inner mould line tools from the part after the at least one spacer(s) have been removed; and removing the inner mould line tools from the part through the at least one of the open ends.
2. A method of manufacturing a wingbox, the method comprising:
arranging a set of components in a set of recesses on one or more inner mould line tools;
forming a layer around the at least one inner mould line tool(s) to form a tubular part with first and second open ends;
laying a first skin onto a first outer mould line tool;
laying a second skin onto a second outer mould line tool;
fitting the first and second outer mould line tools carrying the first and second skins on opposite sides of the at least one inner mould line tool(s) with the first skin positioned between the at least one inner mould line tool and the first outer mould line tool and the second skin positioned between the at least one inner mould line tool and the second outer mould line tool;
moulding the part by compressing the layer, the first and second skins, and the components between the at least one inner mould line tools and the outer mould line tools; and removing the at least one inner mould line tool(s) from the part through at least one of the open ends.
arranging a set of components in a set of recesses on one or more inner mould line tools;
forming a layer around the at least one inner mould line tool(s) to form a tubular part with first and second open ends;
laying a first skin onto a first outer mould line tool;
laying a second skin onto a second outer mould line tool;
fitting the first and second outer mould line tools carrying the first and second skins on opposite sides of the at least one inner mould line tool(s) with the first skin positioned between the at least one inner mould line tool and the first outer mould line tool and the second skin positioned between the at least one inner mould line tool and the second outer mould line tool;
moulding the part by compressing the layer, the first and second skins, and the components between the at least one inner mould line tools and the outer mould line tools; and removing the at least one inner mould line tool(s) from the part through at least one of the open ends.
3. The method of any one of claims 1 or 2 wherein the part is a wing-box.
4. The method of any one of claims 1, 2 or 3 wherein the layer is formed by wrapping around the or each inner mould line tool.
5. The method of claim 4 wherein the or each inner mould line tool is rotated as the layer is wrapped around the inner mould line tool(s).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0616121.0 | 2006-08-14 | ||
| GBGB0616121.0A GB0616121D0 (en) | 2006-08-14 | 2006-08-14 | Moulding tool and method of manufacturing a part |
| PCT/GB2007/002819 WO2008020158A2 (en) | 2006-08-14 | 2007-07-25 | Moulding tool and method of manufacturing a part bonding for example spars on a skin |
Publications (2)
| Publication Number | Publication Date |
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| CA2660964A1 CA2660964A1 (en) | 2008-02-21 |
| CA2660964C true CA2660964C (en) | 2015-12-01 |
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| CA2660964A Expired - Fee Related CA2660964C (en) | 2006-08-14 | 2007-07-25 | Moulding tool and method of manufacturing a part |
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| EP (2) | EP2051838A2 (en) |
| JP (2) | JP5301440B2 (en) |
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| GB (1) | GB0616121D0 (en) |
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| JP2013230687A (en) | 2013-11-14 |
| CN101500773A (en) | 2009-08-05 |
| US9481115B2 (en) | 2016-11-01 |
| JP5770786B2 (en) | 2015-08-26 |
| US20100000667A1 (en) | 2010-01-07 |
| CA2660964A1 (en) | 2008-02-21 |
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